WO2015156857A3 - Structural arrangement and method of fabricating a composite trailing edge control surface - Google Patents

Structural arrangement and method of fabricating a composite trailing edge control surface Download PDF

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Publication number
WO2015156857A3
WO2015156857A3 PCT/US2015/010967 US2015010967W WO2015156857A3 WO 2015156857 A3 WO2015156857 A3 WO 2015156857A3 US 2015010967 W US2015010967 W US 2015010967W WO 2015156857 A3 WO2015156857 A3 WO 2015156857A3
Authority
WO
WIPO (PCT)
Prior art keywords
control surface
trailing edge
contiguous
edge control
skin
Prior art date
Application number
PCT/US2015/010967
Other languages
French (fr)
Other versions
WO2015156857A2 (en
Inventor
David C. Reusch
Original Assignee
The Boeing Company
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by The Boeing Company filed Critical The Boeing Company
Priority to EP15744717.8A priority Critical patent/EP3126125B1/en
Publication of WO2015156857A2 publication Critical patent/WO2015156857A2/en
Publication of WO2015156857A3 publication Critical patent/WO2015156857A3/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/302—Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/20—Integral or sandwich constructions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/02—Mounting or supporting thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/12—Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C2793/00—Shaping techniques involving a cutting or machining operation
    • B29C2793/0081—Shaping techniques involving a cutting or machining operation before shaping
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C2009/005—Ailerons
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Transportation (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Shaping Of Tube Ends By Bending Or Straightening (AREA)

Abstract

The present disclosure is generally directed to a composite trailing edge control surface (600) including a contiguous one-piece composite control surface skin (200) wrapped around a plurality of stiffening cores (300), a plurality of hinge fittings (400), and a plurality of substantially parallel ribs (500). The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin (200) on a substantially flat tool. A plurality of stiffener cores (300) having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin (350) that is trimmed and has fastener apertures and hinge fitting access apertures (210) provided there-through.
PCT/US2015/010967 2014-04-01 2015-01-12 Structural arrangement and method of fabricating a composite trailing edge control surface WO2015156857A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15744717.8A EP3126125B1 (en) 2014-04-01 2015-01-12 Structural arrangement and method of fabricating a composite trailing edge control surface

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US14/231,975 2014-04-01
US14/231,975 US9981735B2 (en) 2014-04-01 2014-04-01 Structural arrangement and method of fabricating a composite trailing edge control surface

Publications (2)

Publication Number Publication Date
WO2015156857A2 WO2015156857A2 (en) 2015-10-15
WO2015156857A3 true WO2015156857A3 (en) 2015-12-03

Family

ID=53762275

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2015/010967 WO2015156857A2 (en) 2014-04-01 2015-01-12 Structural arrangement and method of fabricating a composite trailing edge control surface

Country Status (3)

Country Link
US (2) US9981735B2 (en)
EP (1) EP3126125B1 (en)
WO (1) WO2015156857A2 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201522327D0 (en) * 2015-12-17 2016-02-03 Airbus Operations Ltd Wing structure
CN106542083B (en) * 2016-11-25 2018-09-25 北京理工大学 A kind of small drone cunning race augmentation control method
CN108146652A (en) * 2016-12-06 2018-06-12 成都凯迪精工科技有限责任公司 A kind of aspect ratio is more than 9 times of rudder face manufacturing method
CN108372402B (en) * 2016-12-21 2019-11-19 中国航空制造技术研究院 The adaptive location device and posture adjustment docking system and control method of big component docking
GB2561851A (en) * 2017-04-25 2018-10-31 Airbus Operations Ltd Fibre reinforced composite aerofoil structures
US10866675B2 (en) * 2019-01-29 2020-12-15 Wuhan China Star Optoelectronics Semiconductor Display Technology Co., Ltd. Force touch display device and force touch control method
US11046420B2 (en) * 2019-10-23 2021-06-29 The Boeing Company Trailing edge flap having a waffle grid interior structure
US11724792B2 (en) 2021-09-14 2023-08-15 Rohr, Inc. Composite airfoil for an aircraft

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0532016A1 (en) * 1991-09-13 1993-03-17 Grumman Aerospace Corporation Composite focused load control surface
US20040145080A1 (en) * 2002-12-25 2004-07-29 Shigeki Tanaka Method for fabricating wing
US20100247838A1 (en) * 2009-03-24 2010-09-30 The Boeing Company Method of making bead-stiffened composite parts and parts made thereby
WO2013005206A1 (en) * 2011-07-05 2013-01-10 Israel Aerospace Industries Ltd. Manufacture of articles formed of composite materials

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6889937B2 (en) * 1999-11-18 2005-05-10 Rocky Mountain Composites, Inc. Single piece co-cure composite wing
US7871040B2 (en) * 2006-11-10 2011-01-18 The Boeing Company Composite aircraft structures with hat stiffeners
CA2757910C (en) * 2009-05-28 2018-01-16 Societe Lorraine De Construction Aeronautique Fabrication method for a composite structural panel for the trailing edge of an aircraft element

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0532016A1 (en) * 1991-09-13 1993-03-17 Grumman Aerospace Corporation Composite focused load control surface
US20040145080A1 (en) * 2002-12-25 2004-07-29 Shigeki Tanaka Method for fabricating wing
US20100247838A1 (en) * 2009-03-24 2010-09-30 The Boeing Company Method of making bead-stiffened composite parts and parts made thereby
WO2013005206A1 (en) * 2011-07-05 2013-01-10 Israel Aerospace Industries Ltd. Manufacture of articles formed of composite materials

Also Published As

Publication number Publication date
US9981735B2 (en) 2018-05-29
WO2015156857A2 (en) 2015-10-15
US20180244366A1 (en) 2018-08-30
EP3126125B1 (en) 2021-10-20
EP3126125A2 (en) 2017-02-08
US20160137287A1 (en) 2016-05-19

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